shore profile

Generate 2D airfoil section coordinates and write them as Selig-format .dat files (the de-facto standard used by the UIUC airfoil database and most CFD pre-processors).

shore profile is a sub-app with one command for now:

shore profile naca DESIGNATION [OPTIONS]

Output is one .dat file with the section's (2 * n_pts - 1, 2) coordinates ordered upper-TE → LE → lower-TE. Compatible with shore body extrude and any UIUC-style consumer.

For the algorithmic detail (NACA 4 vs 5-digit polynomial families, closed vs open TE, cosine sampling), see Algorithm — airfoil profiles.

shore profile naca

Generate a NACA 4-digit or 5-digit airfoil section.

Synopsis

shore profile naca DESIGNATION [OPTIONS]

Arguments

Argument	Description
DESIGNATION	NACA digit string. 4 chars = 4-digit family (0012, 2412); 5 chars = 5-digit family (23012, 23112 reflexed).

Options

Option	Default	Description
-o / --output PATH	— (required)	Output .dat file
--n-pts INTEGER	80	Chord samples per side (LE..TE). The total point count is 2 * n_pts - 1.
--closed-te / --open-te	--closed-te	Apply the small thickness-polynomial adjustment that closes the TE exactly. --open-te leaves the natural ~0.1% chord gap.
--name TEXT	NACA <designation>	First-line name comment in the .dat file

Examples

# Symmetric 12% thickness:
shore profile naca 0012 -o naca0012.dat

# Cambered 4-digit at higher resolution:
shore profile naca 2412 --n-pts 120 -o naca2412.dat

# 5-digit with explicit name:
shore profile naca 23012 -o naca23012.dat --name "NACA 23012 root section"

# Open TE for downstream blunt-TE detection:
shore profile naca 0012 --open-te -o naca0012-blunt.dat

Selig output format

Each line is two whitespace-separated floats. The first line is an optional name comment (skipped on read); the rest are coordinate rows:

NACA 0012
   1.0000000   -0.0000000
   0.9996085    0.0000837
   0.9984318    0.0003342
   ...
   0.0003915   -0.0006611
   1.0000000    0.0000000

Supported designations

The 4-digit family is fully supported. The 5-digit family supports the standard mean lines 21012, 22012, 23012, 24012, 25012 (L = 2, S = 0) and their reflexed counterparts 22112, 23112, 24112, 25112. Other L values (non-standard design CL) are rejected with a clear error. The modified 4-digit (0012-64-style) and 6-series families need additional integrals and aren't implemented in this release.

See also

• shore body extrude — extrude a Selig section into a 3D wing STL.
• Algorithm — airfoil profiles — polynomial derivations.